EP1191188B1 - Wellenanordnung für eine dampfgekühlte Gasturbine - Google Patents

Wellenanordnung für eine dampfgekühlte Gasturbine Download PDF

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Publication number
EP1191188B1
EP1191188B1 EP01120371A EP01120371A EP1191188B1 EP 1191188 B1 EP1191188 B1 EP 1191188B1 EP 01120371 A EP01120371 A EP 01120371A EP 01120371 A EP01120371 A EP 01120371A EP 1191188 B1 EP1191188 B1 EP 1191188B1
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EP
European Patent Office
Prior art keywords
rotor
tail end
thermal
gas turbine
shaft portion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP01120371A
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English (en)
French (fr)
Other versions
EP1191188A3 (de
EP1191188A2 (de
Inventor
Takeaki c/o Takasago Machinery Works Oya
Kazuharu c/o Takasago Machinery Works Hirokawa
Tadateru c/o Takasago Machinery Works Tanioka
Tanehiro c/o Takasago Res.& Devel.Cent Shinohara
Katsunori c/o Takasago Machinery Works Tanaka
Kazuo c/o Takasago Machinery Works Uematsu
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from JP2000292763A external-priority patent/JP4690531B2/ja
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to EP04023741A priority Critical patent/EP1496197B1/de
Priority to EP04023742A priority patent/EP1496198B1/de
Publication of EP1191188A2 publication Critical patent/EP1191188A2/de
Publication of EP1191188A3 publication Critical patent/EP1191188A3/de
Application granted granted Critical
Publication of EP1191188B1 publication Critical patent/EP1191188B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02Blade-carrying members, e.g. rotors
    • F01D5/08Heating, heat-insulating or cooling means
    • F01D5/085Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08Cooling; Heating; Heat-insulation
    • F01D25/12Cooling
    • F01D25/125Cooling of bearings
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02Blade-carrying members, e.g. rotors
    • F01D5/08Heating, heat-insulating or cooling means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00Components
    • F05D2240/60Shafts
    • F05D2240/61Hollow
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/20Heat transfer, e.g. cooling
    • F05D2260/205Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/20Heat transfer, e.g. cooling
    • F05D2260/232Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the present invention relates to prevention or restriction of thermal deformation of a rotor tail end of a steam-cooled gas turbine.
  • the temperature of the burnt gas at an inlet of a gas turbine has been increasing to increase the efficiency of the gas turbine, and in recent years, a gas turbine in which the temperature reaches 1500°C has been proposed.
  • a so-called steam-cooled gas turbine in which the relatively low temperature of steam is used as a coolant, to protect stator blades and rotor blades of the gas turbine from the burnt gas of high temperature, in place of a conventional air cooling system, is being developed.
  • a rotor assembly of a gas turbine having a plurality of rotor disks which are fastened to each other by spindle bolts so as to rotate together is rotatably supported by a journal bearing. Since the rotor assembly of the gas turbine is very heavy, the gap between the shaft portion of the rotor assembly and the journal bearing is very precisely administrated. However, in the steam-cooled gas turbine, the steam passes through the center portion of the rotor assembly and, hence, the latter and in particular its shaft portion is thermally deformed, so that the journal bearing can be damaged.
  • a shaft structure of a rotor tail end of a gas turbine according to the preamble of claim 1 is known.
  • a cylindrical thermal shield shown in figure 4 with reference numeral 3, is provided between the steam passage and the inner surface of the center hole of the rotor tail end.
  • This cylindrical thermal shield is an L-shaped element fixedly secured by means of coupling bolts on the turbine shaft and has a recess forming an annular space between the outer peripheral surface of the thermal shield and the inner peripheral surface of the turbine shaft.
  • thermal shield is not able to absorb the thermal expansion in the axial direction or to reduce the thermal stress arising when a temperature difference between the shaft portion and the thermal sleeve (thermal shield), since the thermal shield is just a solid element which can not absorb thermal expansions or thermal stress.
  • a shaft structure of a rotor tail end of a gas turbine having the features of the preamble of claim 1 is described.
  • the shaft structure has a solid element between the steam passage and the inner surface of the center hole of the rotor tail. This solid element is fixed to the shaft structure and likewise is not able to absorb the thermal expansion in the axial direction or to reduce thermal stress arising when a temperature difference is caused between the shaft portion and the thermal sleeve.
  • a shaft structure of a rotor tail end of a gas turbine in which a steam passage for supplying and recovering a steam for cooling rotor blades of the gas turbine extends along a center axis of the rotor assembly of the gas turbine, wherein a center hole of the rotor tail end coaxial to the center axis of the steam passage is formed in the rotor tail end; a thermal sleeve is provided between the steam passage and the inner surface of the center hole of the rotor tail end; a thermal insulation gas layer is formed between the inner surface of the center hole of the rotor tail end and the thermal sleeve; and the thermal insulation gas layer is isolated gas-tightly and liquid-tightly from the outside.
  • the thermal insulation gas layer is gas-tightly or liquid-tightly isolated from the outside, no steam enters the thermal insulation gas layer. Therefore, if the temperature drops during the stoppage of the gas turbine, no drain of the steam due to the condensation thereof occurs. Thus, no abnormal vibration due to the drain of the steam takes place.
  • the thermal sleeve is in the form of a substantially circular cylinder which is welded at its one end to an end disk of the gas turbine and welded at the other end to the shaft portion of the rotor tail end and the thermal sleeve is provided with a bent portion in the vicinity of the end thereof welded to the shaft portion of the rotor tail end, so that the bent portion reduces a thermal stress due to a thermal expansion of the thermal sleeve.
  • the bent portion absorbs the thermal expansion in the axial direction due to the temperature difference to thereby prevent the thermal sleeve from being damaged or broken.
  • a pre-tension is preferably applied to the thermal sleeve.
  • the welding of the pre-tensed thermal sleeve to the shaft portion prevents the occurrence of thermal deformation of the thermal sleeve.
  • the bent portion and the application of the pre-tension contributes, in combination, to further restriction of the thermal deformation of the thermal sleeve and to a prevention of the thermal sleeve from being damaged or broken.
  • a shaft structure of a rotor tail end of a gas turbine in which a steam passage for supplying and recovering a steam for cooling rotor blades of the gas turbine extends along a center axis of the rotor assembly of the gas turbine, wherein said rotor tail end is provided therein with a center hole coaxial to the center axis of the steam passage; a thermal sleeve is provided between the steam passage and the inner surface of the center hole of the rotor tail end; a thermal insulation gas layer is formed between the inner surface of the center hole of the rotor tail end and the thermal sleeve; and cooling air is circulated from the outside into the thermal insulation gas layer to enhance the cooling effect of the rotor.
  • the thermal sleeve is in the form of a substantially circular cylinder which is welded at its one end to an end disk of the gas turbine and is welded at the other end to a shaft portion of the rotor tail end through a bellows which reduces a thermal stress due to a thermal expansion of the thermal sleeve.
  • Fig. 4 shows a known supply/recovery system of the cooling steam for rotor blades of a turbine.
  • the structure of the gas turbine rotor on the turbine side is completed by fastening a rotor tail end and a plurality of turbine disks.
  • the rotor tail end is provided with a center hole to define a coaxial steam pipe.
  • the rotor tail end 100 is provided with a substantially circular disk portion 120 which defines an end disk and a substantially cylindrical hollow shaft portion 140.
  • a disk center hole 130 and a rotor tail end center hole 150 extend along the central axis.
  • the disk portion 120 is provided with a plurality of through holes (not shown) which are spaced from one another in the circumferential direction at an equal distance.
  • a plurality of rotor blade disks (not shown) of the turbine are arranged in front of the disk portion 120 and, thereafter, turbine spindle bolts (not shown) are inserted in the through holes and fastened by nuts to form a rotor assembly in which the rotor blade disks (not shown) are supported and rotated together.
  • the disk center hole 130 of the rotor is provided with a steam passage member 200 welded thereto, through which the rotor blade cooling steam is supplied.
  • a passage to recover the steam for cooling the rotor blade is defined between the inner surface of the central hole 150 of the rotor tail end extending from the rear end of the end disk of the rotor into the shaft portion 140 of the rotor and the steam passage member, so that the steam used to cool the rotor blades by means of an appropriate cooling device (not shown) can be recovered.
  • the connection between the rotating rotor tail end 100 and the stationary part is established as follows.
  • the steam passage member 200 is connected to a stationary inner steam pipe 290 through a seal fin (labyrinth seal) 230.
  • a stationary short steam pipe 270 and an outer stationary steam pipe 280 are connected to the end of the rotor tail end 100 through a seal fin (labyrinth seal) 220.
  • the seal fins 220 and 230 are connected to a leakage steam recovery instrument (not shown).
  • the rotor assembly thus obtained is rotatably supported at the rotor tail end 100 thereof by a bearing 240.
  • the rotor blade cooling steam is produced by heating pressurized steam whose saturation temperature is approximately 140°C to 400°C or more, and is supplied through the passageway defined by the center hole of the rotor. Consequently, the rotor is heated to the saturation temperature of the cooling steam.
  • the tail end at which the bearing is provided is cooled by the lubricant to 100°C or less than 100°C, so that thermal deformation of the tail end occurs due to a temperature difference between the central hole and the tail end.
  • Fig. 1 shows a sectional view of a half of a tail end 10 of a rotor assembly of a gas turbine (which will be referred to merely as a rotator tail end), according to an embodiment of the invention.
  • the compressor side of the gas turbine is referred to as a front side (left side in Fig. 1) and the expansion device side is referred to as a rear side (right side in Fig. 1).
  • the rotor tail end 10 includes an end disk 12 in the form of a substantially circular disk having a disk center hole 13 and a substantially cylindrical hollow shaft portion 14.
  • a steam passage member 20 for supplying cooling steam is welded to the disk center hole 13.
  • the end disk 12 is provided with a plurality of through holes 12b (not shown) which are spaced at an equal distance in the circumferential direction about the center axis O in the longitudinal direction of the rotor assembly.
  • Turbine spindle bolts (not shown) are inserted in the through holes 12b while the end disk 12 is in contact at its front end surface 12a with another disk (not shown) and the turbine spindle bolts are fastened by nuts (not shown), so that a rotor assembly which rotates as a unit, while supporting turbine rotor blades (not shown) is formed.
  • the rotor assembly constructed as above is rotatably supported at the rotor tail end 10 by a bearing 24.
  • the bearing 24 is comprised of a bearing pad 24a, and seal portions 26 provided on opposite sides of the bearing pad 24a.
  • the bearing 24 forms a journal bearing.
  • the seal portions 26 include brackets 26a which are adapted to mount seal members 26c to the bearing pad 24a.
  • the rotor tail end 10 is provided with a rotor tail end center hole 15 which is coaxial with the disk center hole 13 and whose diameter is greater than the diameter of the disk center hole 13.
  • a cylindrical thermal sleeve 16 is inserted in the rotor tail end center hole 15.
  • the front end of the thermal sleeve 16 (left end in Fig. 1) is welded to the rotor tail end center hole 15 and the rear end (right end in Fig. 1) is welded to the rear end of the shaft portion 14.
  • the outer diameter of the thermal sleeve 16 is smaller than the inner diameter of the rotor tail end center hole 15 and a thermal insulation gas layer 18 is formed therebetween.
  • the thermal insulation gas layer 18 is filled with dry gas or inert gas such as air or argon.
  • the thermal sleeve 16 is provided on its rear end with a bent portion 16a which is adapted to absorb the thermal stress and in particular the compression stress when a temperature difference is caused between the shaft portion 14 and the thermal sleeve 16 whose temperature is increased in accordance with the operation of the gas turbine. More preferably, the thermal sleeve 16 is welded to the shaft portion 14 while the thermal sleeve is tensed in the axial direction so that a pre-tension is applied thereto. Consequently, when a temperature difference is caused between the thermal sleeve 16 and the shaft portion 14, in accordance with operation of the gas turbine, the compression stress can be reduced.
  • the thermal sleeve 16 is inserted between the steam passage member 20 and the shaft portion 14 so that the thermal insulation gas layer 18 is formed between the thermal sleeve 16 and the inner surface of the rotor tail end center hole 15 of the shaft portion 14. Consequently, when the gas turbine operates and the cooling steam for cooling the turbine rotor blades flows, the heat transfer to the shaft portion 14 is restricted, thus resulting in no or little thermal deformation of the shaft portion 14.
  • the thermal sleeve 16 is welded to the shaft portion 14 with a pre-tension, the thermal stress caused in the thermal sleeve 16 is reduced and thus the deformation thereof can be prevented.
  • the thermal sleeve 16 is provided with the bent portion 16a at the rear end thereof, the thermal stress which cannot be absorbed by the application of the pre-tension can be absorbed by the deformation of the bent portion 16a. Thus, deformation of the cylindrical portion of the thermal sleeve 16 can be avoided.
  • the thermal insulation gas layer 18 is isolated gas-tightly and liquid-tightly from the outside, so that no steam can enter from the outside. Moreover, since the thermal insulation gas layer 18 is filled with a dry gas, no drain due to the condensation of the steam occurs even if the temperature drops during the stoppage of the gas turbine.
  • the rotor tail end 10 is comprised of a substantially circular end disk 12 having a disk center hole 13, and a substantially cylindrical hollow shaft portion 14.
  • a cooling steam supply passage member 20 is welded to the disk center hole 13.
  • the end disk 12 is provided with a plurality of through holes 12b (not shown) which are spaced at an equal distance in the circumferential direction about the longitudinal center axis O of the rotor assembly.
  • Turbine spindle bolts (not shown) are inserted in the through holes while the disk portion 12 is in contact at its front end surface 12a with another disk (not shown), and the turbine spindle bolts are fastened by nuts (not shown), so that a rotor assembly which supports the turbine rotor blades (not shown) and rotates together therewith is formed.
  • the rotor assembly thus obtained is rotatably supported at the tail end 10 by the bearing 24.
  • the bearing 24 is comprised of a bearing pad 24a and seal portions 26 on opposite sides of the bearing pad 24a.
  • the bearing 24 forms a journal bearing as is well known in the field of gas turbines.
  • the seal portions 26 include brackets 26a to mount the seal members 26c to the bearing pad 24a.
  • a cylindrical thermal sleeve 16 is inserted in the rotor tail end center hole 15 of the rotor tail end 10.
  • the rotor tail end center hole 15 is coaxial to the disk center hole 13 and has a diameter greater than the diameter of the disk center hole 13.
  • the front end of the thermal sleeve 16 (left end in Fig. 2) is welded to the rotor tail end center hole 15 and the rear end (right end in Fig. 2) thereof is welded to the rear end of the shaft portion 14.
  • the thermal sleeve 16 has an outer diameter smaller than the inner diameter of the rotor tail end center hole 15 of the shaft portion 14, so that a thermal insulation gas layer 18 is formed therebetween.
  • the thermal sleeve 16 is provided on its rear end with a bent portion 16a which is adapted to absorb the thermal stress and in particular the compression stress when a temperature difference is caused between the shaft portion 14 and the thermal sleeve 16 whose temperature is increased in accordance with the operation of the gas turbine. More preferably, the thermal sleeve 16 is welded to the shaft portion 14 while the thermal sleeve is tensed in the axial direction so that a pre-tension is applied thereto. Consequently, when a temperature difference is caused between the thermal sleeve 16 and the shaft portion 14, in accordance with the gas turbine, the compression stress can be reduced.
  • the shaft portion 14 is provided with a plurality of shaft portion cooling air passages which are comprised of radially extending:cooling air inlet passages 31a and cooling air outlet passages 31c and which are connected to the thermal insulation gas layer 18 to form a cooling air passageway.
  • a cooling air introduction device 32 is provided to face the cooling air inlet passages 31a.
  • the cooling air introduction device 32 is comprised of an air introduction portion 32a provided on a stationary part of the gas turbine, such as a casing (not shown), and a seal member 32b provided on the inner surface of the air introduction portion 32a.
  • the air introduction portion 32a and the seal member 32b are respectively provided with a plurality of air passages 32c and 32d which are connected to the cooling air inlet passages 31a and which are spaced at an equal distance in the circumferential direction, so that the cooling air supplied from the cooling air supply source (not shown) can be introduced into the cooling air inlet passages 31a.
  • a cooling air discharge device 33 is provided to face the cooling air outlet passages 31c.
  • the cooling air discharge device 33 is comprised of an air discharge portion 33a provided on the stationary part of the gas turbine, such as the casing, and a seal member 33b provided on the inner surface of the air discharge portion 33a.
  • the air discharge portion 33a and the seal portion 33b are respectively provided with a plurality of air passages 33c and 33d which are connected to the cooling air outlet passages 31c and which are spaced at an equal distance in the circumferential direction.
  • the air from the cooling air introduction device 32 is fed to the shaft portion cooling air passages 31a, 18 and 31c to cool the rotor tail end 10 and is discharged to the outside of the gas turbine.
  • the shaft portion 14 is provided with a plurality of shaft portion cooling air passages 31a, 18 and 31c in which the cooling air can be passed, when the turbine rotor blade cooling steam flows in the steam passage member 20 in accordance with the operation of the gas turbine, the bearing region of the shaft portion 14 is cooled by the cooling air which passes in the shaft portion cooling air passages 31a, 18 and 31c and, thus, a thermal deformation of the shaft portion 14 can be reduced or restricted.
  • the rotor tail end 10 is comprised of a substantially circular end disk 12 having a disk center hole 13, and a substantially cylindrical hollow shaft portion 14.
  • a cooling steam supply passage member 20 is welded to the disk center hole 13.
  • the end disk 12 is provided with a plurality of through holes 12b (not shown) which are spaced at an equal distance in the circumferential direction about the longitudinal center axis O of the rotor assembly.
  • Turbine spindle bolts (not shown) are inserted in the through holes while the disk portion 12 is in contact at its front end surface 12a with another disk (not shown), and the turbine spindle bolts are fastened by nuts (not shown), so that a rotor assembly which supports the turbine rotor blades (not shown) and rotates together therewith is formed.
  • the rotor assembly thus obtained is rotatably supported at the tail end 10 by the bearing 24.
  • the bearing 24 is comprised of a bearing pad 24a and seal portions 26 on opposite sides of the bearing pad 24a.
  • the bearing 24 forms a journal bearing as is well known in the field of gas turbines.
  • the seal portions 26 are provided with brackets 26a to mount the seal members 26c to the bearing pad 24a.
  • a cylindrical thermal sleeve 16 is inserted in the rotor tail end center hole 15 of the rotor tail end 10.
  • the rotor tail end center hole 15 is coaxial to the disk center hole 13 and has a diameter greater than the diameter of the disk center hole 13.
  • the front end of the thermal sleeve 16 (left end in Fig. 3) is welded to the rotor tail end center hole 15 and the rear end (right end in Fig. 3) thereof is welded to the rear end of the shaft portion 14.
  • the thermal sleeve 16 has an outer diameter smaller than the inner diameter of the rotor tail end center hole 15 of the shaft portion 14, so that a thermal insulation gas layer 18 is formed therebetween.
  • the thermal sleeve 16 is provided on its rear end with a bellows 16b which is adapted to absorb the thermal stress and in particular the compression stress when a temperature difference is caused between the shaft portion 14 and the thermal sleeve 16 whose temperature is increased in accordance with the operation of the gas turbine.
  • the bellows 16b is provided on its ends with flanges which are in turn provided with holes in which mounting bolts are inserted to mount the bellows 16b to the thermal sleeve 16 and the shaft.
  • seal members such as O-rings or C-seal members (not shown) are provided between the flanges of the bellows and the thermal sleeve and between the flanges of the bellows and the shaft to more reliably insulate the thermal insulation gas layer 18 in the gas-tightly and liquid-tightly from the outside.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sliding-Contact Bearings (AREA)
  • Sealing Devices (AREA)

Claims (3)

  1. Wellenstruktur eines Rotorhinterendes (10) einer Gasturbine mit:
    einer Rotoranordnung der Gasturbine mit einer Mittelachse (O);
    Rotorschaufeln der Gasturbine;
    einem Dampfdurchlass (20), der sich entlang der Mittelachse (O) erstreckt, zum Zuführen und Rückgewinnen von Dampf zum Kühlen der Rotorschaufeln;
    einem Rotorhinterende (10) mit einem Wellenteil (14), in dem ein mittleres Loch (15) des Rotorhinterendes (10) koaxial zur Mittelachse (O) des Dampfdurchlasses ausgebildet ist;
    einer Wärmehülse (16), die zwischen dem Dampfdurchlass und der Innenfläche des mittleren Lochs (15) des Rotorhinterendes (10) vorgesehen ist; und
    einer Wärmeisolationsgasschicht (18), die zwischen der Innenfläche des mittleren Lochs (15) des Rotorhinterendes (10) und der Wärmehülse (16) ausgebildet ist;
    wobei die Wärmeisolationsgasschicht (18) gasdicht und flüssigkeitsdicht von der Außenseite isoliert ist,
    dadurch gekennzeichnet, dass
    die Wärmehülse (16) in Form eines im wesentlichen kreisförmigen Zylinders vorliegt, der an einem Ende an eine Endscheibe (12) der Gasturbine geschweißt ist und am anderen Ende an den Wellenteil (14) des Rotorhinterendes (10) geschweißt ist,
    wobei die Wärmehülse (16) mit einem gebogenen Teil (16a) in der Nähe von deren Ende versehen ist, welcher an den Wellenteil (14) des Rotorhinterendes (10) geschweißt ist, so dass der gebogene Teil (16a) eine Wärmebeanspruchung aufgrund einer Wärmeausdehnung der Wärmehülse (16) verringert.
  2. Wellenstruktur eines Rotorhinterendes einer Gasturbine nach Anspruch 1, wobei eine Vorspannung auf die Wärmehülse (16) aufgebracht wird, wenn die letztere an der Endscheibe (12) oder am Wellenteil (14) montiert wird.
  3. Wellenstruktur eines Rotorhinterendes (10) einer Gasturbine mit:
    einer Rotoranordnung der Gasturbine mit einer Mittelachse (O); Rotorschaufeln der Gasturbine;
    einem Dampfdurchlass (20), der sich entlang der Mittelachse (O) erstreckt, zum Zuführen und Rückgewinnen von Dampf zum Kühlen der Rotorschaufeln;
    einem Rotorhinterende (10) mit einem Wellenteil (14), in dem ein mittleres Loch (15) koaxial zur Mittelachse (O) des Dampfdurchlasses (20) ausgebildet ist;
    einer Wärmehülse (16), die zwischen dem Dampfdurchlass (20) und der Innenfläche des mittleren Lochs (15) des Rotorhinterendes (10) vorgesehen ist; und
    einer Wärmeisolationsgasschicht (18), die zwischen der Innenfläche des mittleren Lochs (15) des Rotorhinterendes und der Wärmehülse (16) ausgebildet ist;
    wobei Kühlluft von außen in die Wärmeisolationsgasschicht (18) zirkuliert wird,
    dadurch gekennzeichnet, dass
    die Wärmehülse (16) in Form eines im wesentlichen kreisförmigen Zylinders vorliegt, der an einem Ende an eine Endscheibe (12) der Gasturbine geschweißt ist und am anderen Ende an den Wellenteil (14) des Rotorhinterendes (10) über einen Faltenbalg (16b) geschweißt ist, der eine Wärmebeanspruchung aufgrund einer Wärmeausdehnung der Wärmehülse (16) verringert.
EP01120371A 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine Expired - Lifetime EP1191188B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP04023741A EP1496197B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine
EP04023742A EP1496198B1 (de) 2000-09-26 2001-08-25 Wellen- und Lageranordnung für eine dampfgekühlte Gasturbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2000292763 2000-09-26
JP2000292763A JP4690531B2 (ja) 1999-09-27 2000-09-26 ガスタービンのロータ尾端部の軸構造

Related Child Applications (2)

Application Number Title Priority Date Filing Date
EP04023741A Division EP1496197B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine
EP04023742A Division EP1496198B1 (de) 2000-09-26 2001-08-25 Wellen- und Lageranordnung für eine dampfgekühlte Gasturbine

Publications (3)

Publication Number Publication Date
EP1191188A2 EP1191188A2 (de) 2002-03-27
EP1191188A3 EP1191188A3 (de) 2003-11-19
EP1191188B1 true EP1191188B1 (de) 2006-02-08

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Application Number Title Priority Date Filing Date
EP04023741A Expired - Lifetime EP1496197B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine
EP04023742A Expired - Lifetime EP1496198B1 (de) 2000-09-26 2001-08-25 Wellen- und Lageranordnung für eine dampfgekühlte Gasturbine
EP01120371A Expired - Lifetime EP1191188B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine

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Application Number Title Priority Date Filing Date
EP04023741A Expired - Lifetime EP1496197B1 (de) 2000-09-26 2001-08-25 Wellenanordnung für eine dampfgekühlte Gasturbine
EP04023742A Expired - Lifetime EP1496198B1 (de) 2000-09-26 2001-08-25 Wellen- und Lageranordnung für eine dampfgekühlte Gasturbine

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US (1) US6688847B2 (de)
EP (3) EP1496197B1 (de)
CA (1) CA2356479C (de)
DE (3) DE60132642T2 (de)

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US7090393B2 (en) * 2002-12-13 2006-08-15 General Electric Company Using thermal imaging to prevent loss of steam turbine efficiency by detecting and correcting inadequate insulation at turbine startup
FR2892148B1 (fr) * 2005-10-19 2011-07-22 Snecma Fourreau d'arbre de turboreacteur et turboreacteur comportant ce fourreau
JP5129633B2 (ja) * 2008-03-28 2013-01-30 三菱重工業株式会社 冷却通路用カバーおよび該カバーの製造方法ならびにガスタービン
US10495353B2 (en) * 2012-05-28 2019-12-03 The University Of Western Ontario Mechanism for enhanced energy extraction and cooling of pressurized gas at low flow rates
US20140010648A1 (en) * 2012-06-29 2014-01-09 United Technologies Corporation Sleeve for turbine bearing stack
US20140119887A1 (en) * 2012-11-01 2014-05-01 United Technologies Corporation Fluid-cooled seal arrangement for a gas turbine engine
US9932860B2 (en) 2013-03-13 2018-04-03 United Technologies Corporation Oil transfer passage arrangement for a shaft of a gas turbine engine
CN109113809B (zh) * 2018-09-17 2023-09-19 苏州制氧机股份有限公司 气体轴承透平膨胀机
US11193389B2 (en) 2019-10-18 2021-12-07 Raytheon Technologies Corporation Fluid cooled seal land for rotational equipment seal assembly
KR20200081345A (ko) 2020-06-08 2020-07-07 (주)퍼니랜드 무인 자판기
CN114013818B (zh) * 2021-11-17 2023-07-04 嘉利特荏原泵业有限公司 一种汽轮机转子用运输和储存容器

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JPH07139635A (ja) * 1993-11-18 1995-05-30 Fuji Electric Co Ltd 回転機械軸受台のシールリング
JP3567065B2 (ja) * 1997-07-31 2004-09-15 株式会社東芝 ガスタービン
US6224327B1 (en) * 1998-02-17 2001-05-01 Mitsubishi Heavy Idustries, Ltd. Steam-cooling type gas turbine
JP4308388B2 (ja) * 1998-12-18 2009-08-05 ゼネラル・エレクトリック・カンパニイ タービンロータを蒸気冷却するためのボアチューブアセンブリ
JP4527824B2 (ja) 1998-12-22 2010-08-18 ゼネラル・エレクトリック・カンパニイ タービンロータの軸受用冷却系

Also Published As

Publication number Publication date
EP1496197B1 (de) 2008-11-26
DE60117077T2 (de) 2006-07-13
EP1191188A3 (de) 2003-11-19
US6688847B2 (en) 2004-02-10
EP1191188A2 (de) 2002-03-27
DE60132642T2 (de) 2008-05-21
EP1496198A2 (de) 2005-01-12
CA2356479A1 (en) 2002-03-26
CA2356479C (en) 2005-07-19
EP1496198B1 (de) 2008-01-23
DE60117077D1 (de) 2006-04-20
EP1496198A3 (de) 2005-01-19
EP1496197A1 (de) 2005-01-12
DE60136753D1 (de) 2009-01-08
US20020037216A1 (en) 2002-03-28
DE60132642D1 (de) 2008-03-13

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